CN110177928A - Stream mixer with variable thickness - Google Patents

Stream mixer with variable thickness Download PDF

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Publication number
CN110177928A
CN110177928A CN201880006671.5A CN201880006671A CN110177928A CN 110177928 A CN110177928 A CN 110177928A CN 201880006671 A CN201880006671 A CN 201880006671A CN 110177928 A CN110177928 A CN 110177928A
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CN
China
Prior art keywords
lobe
mixer
wall thickness
modified
thickness
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Granted
Application number
CN201880006671.5A
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Chinese (zh)
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CN110177928B (en
Inventor
雷米·奥利维尔·帕格尼
阿兰·保罗·迈德克
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of CN110177928A publication Critical patent/CN110177928A/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
    • F02K1/48—Corrugated nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/38—Introducing air inside the jet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/73—Shape asymmetric
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

The present invention relates to the concentric gas stream mixers in a kind of multi-flow type turbine, mixer includes upstream portion and the downstream part of general cylindrical, downstream part has the outer lobe and interior lobe being distributed in outside around the tower of the mixer, it is characterized in that, mixer includes at least one modified lobe, modified lobe has the wall thickness of the wall thickness different from other lobes at least one area, to modify the vibratory response of the mixer.

Description

Stream mixer with variable thickness
Technical field
The present invention relates to a kind of stream mixers for multi-flow type turbojet.
Background technique
In multi-flow type (especially double-current method) turbojet, the turbojet that is blended in of mainstream and Secondary Flow is sent out It is carried out in the downstream part of motivation.Wander back to, mainstream is the stream of hot air across combustion chamber.Secondary Flow is for itself It is the cold air stream promoted by fan.The Secondary Flow is around stream of hot air in the shell comprising compression step, combustion chamber and turbine It is concentrically flowed between the hood of turbojet.
The mixing of two kinds of streams has the advantages that multiple: reducing the noise of gas injection, increases thrust and turbojet Whole efficiency.
An example of mixer is described in patent FR2.875.854.In general, this mixer has on the periphery thereof A series of ripples.The circumferentially distributed outer lobe and interior lobe of multiple longitudinal axis around mixer is collectively formed in these ripples.
According to the type for the turbojet for being equipped with mixer thereon, usually not to the turbojet Same geometric shape parameters (length and diameter, radius of curvature of lobe of mixer etc.) are modified, dynamic to optimize air The mixing of mechanical property and stream.
These modifications can have an impact the dynamic characteristic of mixer.
For example, the increase of the radius of curvature of the lobe of the extension and mixer of the length of mixer can lead to component Rigidity reduces, to reduce the frequency of the eigentone of the mixer.
When certain stable speeds of service of these vibration modes and turbojet match, by mixer Deformation may be dangerous for the structurally and mechanically intensity of the mixer caused by vibratory response.
This shows in Fig. 1 a, Fig. 1 b and Fig. 2 a, Fig. 2 b.
With reference to Fig. 1 a, the vibration frequency conduct generated in mixer 1 is shown to the research of Campbell (Campbell) figure The function of the speed of service of turbojet and change, be highlighted two kinds of pure diameter natural modes with by helical turbine The matching of vibration frequency caused by certain speeds of service of paddle motor.
The line of two decline corresponds to the intrinsic frequency of two kinds of pure diameter vibratory modes of 0 Φ type.
Such vibration mode causes the radial deformation of the component in some regions of mixer and tangentially becomes Shape.
The distribution of the deformation indicated in Fig. 1 b shows overwhelming majority deformation and is located on column 0, and this distribution characterizes 0 Φ type Pure mode.
It is such to deform circular expander and the contraction for continuously causing component.
The vibration frequency of the mixer as caused by the operation of turbojet and two kinds of pure diameter natural mode phases Matching, especially in frequency corresponding with one of the stable operational mode of turbojet mode 12 (by Vertical line indicates) match.
With reference to Fig. 2 a, the research of the Campbell chart of mixer 1 is highlighted and is started in mixer 1 by turbojet The matching of two kinds of pure diameter modes of vibration frequency caused by the operation of machine and 1 Φ type.
Such vibratory response causes radial deformation and the tangential deformation of component, the component shown in figure 2b The distribution of radial deformation and tangential deformation continuously causes the expansion and contraction of ellipse.All deformations are all located on column 1, this The pure mode of kind distribution 1 Φ type of characterization.
The pure diameter mode of one of these pure diameter modes is corresponding for the stable speed of service with aircraft Frequency and realize.
Summary of the invention
General purpose of the invention is to make the vibratory response of mixer to minimize.
Another object is to limit mixer gain of quality intrinsic in its structural modification.
According on one side, the invention proposes a kind of mixer for the concentric gas stream in multi-flow type turbine, The mixer includes upstream portion and the downstream part of general cylindrical, which has on the circumference of the mixer Circumferentially distributed outer lobe and interior lobe, which is characterized in that the mixer includes that at least one is set with aperiodicity angular pattern The modified lobe set, the modified lobe have the wall of the wall thickness different from other lobes at least at a region Thickness, to modify the vibratory response of the mixer.
This mixer is completed advantageous by independent use or combination using following different characteristic:
Modified lobe has the wall thickness changed between the 110% to 300% of the wall thickness of conventional lobe；
Modified lobe has the thickness of 1.5mm；
Modified lobe has the wall thickness changed between the 50% to 90% of the wall thickness of conventional lobe；Certainly, if Mixer further includes that at least one has the modified of the wall thickness changed between the 110% to 300% of the wall thickness of conventional lobe Lobe, then the lobe and those there are the lobes of wall thickness changed between the 50% to 90% of the wall thickness of conventional lobe not Together；
Mixer includes at least two modified lobes；
The addition or removal of material expand in whole region, which includes interior half lobe, outer lobe and interior half Lobe；
Modified lobe has the construction for the wall thickness for being designed to generate complex vibration mode；
- two lobes with the setting of aperiodicity angular pattern have different wall thickness.
The present invention relates to a kind of turbines including this mixer according to another aspect,.
Detailed description of the invention
According to only illustrative and unrestricted and should refer to the following explanation of attached drawing reading, of the invention its He will be apparent feature and advantage, in the accompanying drawings:
- Fig. 1 a is the graphical representation of Campbell chart, be highlighted the pure diameter natural mode of 0 Φ type mixer with by The matching of turbojet caused vibration during the stable speed of service, Fig. 1 b are prominent in the Campbell chart of Fig. 1 a The histogram of deformation distribution encountered in one of natural mode of display indicates；
- Fig. 2 a is the graphical representation of Campbell chart, be highlighted the pure diameter natural mode of 1 Φ type mixer with by The matching of turbojet caused vibration during the stable speed of service, Fig. 2 b are prominent in the Campbell chart of Fig. 2 a The histogram of deformation distribution encountered in one of natural mode of display indicates；
- Fig. 3 shows the profile of turbojet and constitutes the schematic of the element of the turbojet Sectional view；
- Fig. 4 a, Fig. 4 b and Fig. 4 c are the 3D modelings for the stream mixer observed with different view；
- Fig. 5 a and determine Figure 5b shows that the deformation when mixer of the pure diameter mode for the 0 Φ type models Position and type；
- Fig. 6 a and Fig. 6 b show the amplitude of the deformation of complex vibration mode and position on mixer；
- Fig. 7 a and Fig. 7 b show the 3D modeling of mixer, suffered modification are highlighted, to modify the mixing The vibratory response of device.
Specific embodiment
Overview
With reference to Fig. 3, double-flow turbine jet engine T (it is considered as known general operation that it, which will not be described again) is usually It is from upstream to the fan that downstream has actuating air stream, which will be divided into mainstream Fp and Secondary Flow Fs.
Mainstream flows in low pressure compressor, high pressure compressor, combustion chamber, high-pressure turbine Thp and in the downstream of mixer 1 Converge Secondary Flow Fs.
Secondary Flow Fs surrounds inner housing Ci for itself and concentrically flows inside outer housing Ce with mainstream Fp.
The function of mixer 1 is that the mixing to the mainstream Fp and Secondary Flow Fs in the exit of turbojet T carries out Optimization.
In terms of performance and environmental disturbances, mainstream Fp is mixed with Secondary Flow Fs in the downstream of turbojet T Many advantages are brought, explore new solution constantly to optimize uniformity of mixture.
Flow mixer
With reference to Fig. 4 a, Fig. 4 b and Fig. 4 c, the lobed mixer 1 of chrysanthemum lobe type has the upstream portion 2 of general cylindrical With undulatory downstream part 3.
About the axis for radially, axially corresponding to mixer with the instruction of tangential direction, which is also turbojet hair The axis of motivation.Upstream and downstream concept follows flow direction of the gas in turbojet.
The circumferentially distributed radial outer lobe 4 of multiple longitudinal axis around mixer 1 is collectively formed in the ripple of downstream part With interior lobe 5.
Mixer, which has the property that at least one lobe at least one area, to be had the addition of material or removes, The addition of the material removes and is configured to modify to the vibratory response of the mixer.
It selects the addition or takes out to change the frequency of the natural mode of the mixer, to avoid sending out with by turbojet Vibration frequency caused by the stable speed of service of motivation matches.
Particularly, in order to reduce vibratory response, as will later be shown, the modification that mixer 1 carries out is intended to promote by pure mould The appearance for the complex patterns that the summation of formula is constituted.
The embodiment of mixer
With reference to Fig. 5 a, the solution of reservation includes two lobes 14 with modified thickness.In fact, in order to make Quality, which increases, to be minimized, and the best compromise between quality increase and vibratory response modification is sought.
Therefore, modified lobe 14 is outer lobe 44, which has thicker surface portion, the part such as Fig. 5 b What is observed in extend between the vertex of two interior lobes 5 having a common boundary the part like that.
Two lobes 14 mentioned above have the wall thickness different from the wall thickness of other lobes 13.In the solution party of reservation In case, mixer 1 includes 16 with the conventional lobe 13 of 1mm wall thickness and 2 particular lobes 14 with 1.5mm wall thickness.
The rate that thickens of keeping wall also contemplates manufacturing constraints, minimum thick to ensure to have in tolerance region on finished product The thick lobe 14 of degree is substantially different from the conventional lobe 13 in tolerance region with maximum gauge, to ensure all mixers 1 substantially constant performance gain.
The thickness of modified lobe 14 can be the 110% to 300% of the thickness of conventional lobe.
For example, modified lobe 14 can have 150% thickness for representing the thickness of conventional lobe 13.
Significant difference allows apparent vision difference during manufacture, by by juxtaposition and half lobe welded together It is assembled to manufacture mixer 1.
During assembly, two distinct types of component makes it possible to produce mixer 1:
- the first seed type is conventional lobe 13, which includes the outer lobe being made of half lobe in two, this The component of seed type mainly forms mixer；
- second type is modified lobe 14, the modified lobe 14 other than the thickness of its wall have with The identical general geometry of conventional lobe, and in fig 5 a shown in the case where solution, include two in mixer 1 Modified complete lobe.
Component is juxtaposed and is welded to form the lobe of mixer.
Contact profile between modified lobe 14 and conventional lobe 13 is unsmooth, thus contact position include with through repairing Thickness difference between the lobe changed and conventional lobe is relevant " ladder ".
Another method for manufacturing mixer is described in document FR2912469.
In other embodiments of the invention, it is further contemplated that, reduce the thickness of lobe to generate identical effect, through repairing The lobe 14 changed has 25% to 90% thickness of the thickness that can represent conventional lobe in this embodiment.
Modified lobe 14 can 50% thickness for example with the thickness for representing conventional lobe 13.
To the thickness of one or more lobes carry out modification once in a while be also it is possible, such as added material or part it is additional Thickness and removal material (hole or groove are formed such as in one or more lobes).
The relative position of modified lobe 14 also influences the vibratory response of mixer 1.In fact, by modified lobe The angle periodically (periodicity rotated along the axis around mixer) that 14 position is formed by pattern promotes intrinsic The appearance of mode.Therefore, one of contemplated solution is to arrange multiple in the case where thickening multiple lobes Lobe forms the duplicate pattern of angle to avoid generating.
With reference to Fig. 5 b, the thicker region of modified lobe 14 is therefore related to outer lobe 4.
Therefore, used to construct the appearance for making it possible to promote complex vibration mode, in addition to greatly reducing with quilt It is considered except the quantity of the mode of pure diameter, also reduces the damage to mixer 1.
Required vibration mode
With reference to Fig. 6 b, the mapping of the deformation under pure deformation pattern (being 0 Φ of mode herein) can be observed.For given half Diameter, modified being generally in the shape of is uniform, realizes maximum distortion at the minimum diameter of component at the wave crest of interior lobe 5.
With reference to Fig. 7 b, it may be noted that represented critical conduction mode be included in diameter of phi 3, Φ 12, Φ 14, Φ 15, Mode at Φ 16, Φ 17, Φ 18, Φ 19, Φ 20 and Φ 21 with radial deformation has at diameter of phi 0, Φ 3 and Φ 6 and cuts The summation of mode to the mode of deformation and at diameter of phi 18 and Φ 21 with axial deformation.In addition to lesser amplitude Except, the distribution of deformation is also less uniformly.

Claims (8)

1. a kind of mixer (1) for the concentric gas stream in multi-flow type turbine, the mixer includes general cylindrical Upstream portion (11) and downstream part (12), the downstream part have it is circumferentially distributed on the circumference of the mixer (1) Outer lobe (4) and interior lobe (5), which is characterized in that the mixer includes that at least one is set with aperiodicity angular pattern The modified lobe (14) set, the modified lobe have the wall thickness different from other lobes at least at a region Wall thickness, to modify the vibratory response of the mixer (1).
2. mixer (1) according to any one of the preceding claims, which is characterized in that at least one is described modified Lobe (14) has the wall thickness changed between the 110% to 300% of the wall thickness of conventional lobe (13).
3. mixer (1) according to any one of the preceding claims, which is characterized in that at least one is described modified Lobe (14) has the thickness of 1.5mm.
4. mixer (1) according to any one of the preceding claims, which is characterized in that at least one is described modified Lobe (14) has the wall thickness changed between the 50% to 90% of the wall thickness of conventional lobe (13).
5. mixer according to any one of the preceding claims, which is characterized in that the mixer includes at least two Modified lobe (14).
6. mixer according to any one of the preceding claims, which is characterized in that the addition or removal of material expand to In whole region, the whole region includes interior half lobe (5), outer lobe (4) and interior half lobe (5).
7. mixer according to any one of the preceding claims, which is characterized in that two with aperiodicity angular pattern The lobe (14) of setting has different wall thickness.
8. a kind of turbine, the turbine includes the mixer according to preceding claims (1).
CN201880006671.5A 2017-01-11 2018-01-11 Flow mixer with varying thickness Active CN110177928B (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1750234A FR3061749B1 (en) 2017-01-11 2017-01-11 FLOW MIXER WITH EVOLUTIVE THICKNESS
FR1750234 2017-01-11
PCT/FR2018/050064 WO2018130787A1 (en) 2017-01-11 2018-01-11 Flow mixer with a changing thickness

Publications (2)

Publication Number Publication Date
CN110177928A true CN110177928A (en) 2019-08-27
CN110177928B CN110177928B (en) 2021-08-13

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CN201880006671.5A Active CN110177928B (en) 2017-01-11 2018-01-11 Flow mixer with varying thickness

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US (1) US11506143B2 (en)
EP (1) EP3568583B1 (en)
CN (1) CN110177928B (en)
CA (1) CA3050019A1 (en)
FR (1) FR3061749B1 (en)
WO (1) WO2018130787A1 (en)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5265807A (en) * 1992-06-01 1993-11-30 Rohr, Inc. Aerodynamic stiffening ring for an aircraft turbine engine mixer
US20050115245A1 (en) * 2003-07-09 2005-06-02 Snecma Moteurs Device for reducing the jet noise of a turbomachine
FR3008740A1 (en) * 2013-07-18 2015-01-23 Snecma TURBOMACHINE COMPRISING A LOBE MIXER BETWEEN A GAS GENERATOR AND A TURBINE.
CN105637206A (en) * 2013-06-28 2016-06-01 埃克森美孚上游研究公司 Clusters of polynomials for data points
CN105697193A (en) * 2014-12-09 2016-06-22 劳斯莱斯公司 Cmc oxide-oxide mixer design

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2875854B1 (en) 2004-09-29 2009-04-24 Snecma Propulsion Solide Sa MIXER FOR TUYERE WITH SEPARATE FLUX
US7966824B2 (en) * 2006-08-09 2011-06-28 The Boeing Company Jet engine nozzle exit configurations and associated systems and methods
US8157207B2 (en) * 2006-08-09 2012-04-17 The Boeing Company Jet engine nozzle exit configurations, including projections oriented relative to pylons, and associated systems and methods
FR2912469B1 (en) 2007-02-12 2009-05-08 Snecma Propulsion Solide Sa METHOD FOR MANUFACTURING A LOBE STRUCTURE OF CMC FLUX MIXER FOR AERONAUTICAL GAS TURBINE ENGINE.
FR3095675B1 (en) * 2019-05-03 2021-04-09 Safran Aircraft Engines Turbomachine Separate Flow Mixer

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5265807A (en) * 1992-06-01 1993-11-30 Rohr, Inc. Aerodynamic stiffening ring for an aircraft turbine engine mixer
US20050115245A1 (en) * 2003-07-09 2005-06-02 Snecma Moteurs Device for reducing the jet noise of a turbomachine
CN105637206A (en) * 2013-06-28 2016-06-01 埃克森美孚上游研究公司 Clusters of polynomials for data points
FR3008740A1 (en) * 2013-07-18 2015-01-23 Snecma TURBOMACHINE COMPRISING A LOBE MIXER BETWEEN A GAS GENERATOR AND A TURBINE.
CN105697193A (en) * 2014-12-09 2016-06-22 劳斯莱斯公司 Cmc oxide-oxide mixer design

Also Published As

Publication number Publication date
FR3061749A1 (en) 2018-07-13
FR3061749B1 (en) 2020-05-01
CA3050019A1 (en) 2018-07-19
EP3568583B1 (en) 2021-08-18
EP3568583A1 (en) 2019-11-20
CN110177928B (en) 2021-08-13
US20190338725A1 (en) 2019-11-07
WO2018130787A1 (en) 2018-07-19
US11506143B2 (en) 2022-11-22

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